Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetric diamond airfoil of semiangle epsilon = 15-degrees at an angle of attack to the free stream of 5-degrees when the upstream Mach number and pressure are 2.0 and 2116 lb/ft2, respectively. The maximum thickness of the airfoil is t = 0.5 ft. Assume a unite length of 1 ft in the spanwise direction.